EP0918153A1 - Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbine à gaz - Google Patents

Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbine à gaz Download PDF

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Publication number
EP0918153A1
EP0918153A1 EP97810903A EP97810903A EP0918153A1 EP 0918153 A1 EP0918153 A1 EP 0918153A1 EP 97810903 A EP97810903 A EP 97810903A EP 97810903 A EP97810903 A EP 97810903A EP 0918153 A1 EP0918153 A1 EP 0918153A1
Authority
EP
European Patent Office
Prior art keywords
fuel
injection
burner
head stage
emission
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP97810903A
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German (de)
English (en)
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EP0918153B1 (fr
Inventor
Erfindernennung liegt noch nicht vor Die
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
ABB Research Ltd Switzerland
Alstom Schweiz AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication date
Application filed by ABB Research Ltd Switzerland, Alstom Schweiz AG filed Critical ABB Research Ltd Switzerland
Priority to EP97810903A priority Critical patent/EP0918153B1/fr
Priority to DE59711378T priority patent/DE59711378D1/de
Publication of EP0918153A1 publication Critical patent/EP0918153A1/fr
Application granted granted Critical
Publication of EP0918153B1 publication Critical patent/EP0918153B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N1/00—Regulating fuel supply
    • F23N1/005—Regulating fuel supply using electrical or electromechanical means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B51/00—Other methods of operating engines involving pretreating of, or adding substances to, combustion air, fuel, or fuel-air mixture of the engines
    • F02B51/06—Other methods of operating engines involving pretreating of, or adding substances to, combustion air, fuel, or fuel-air mixture of the engines involving rays or sound waves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/16—Systems for controlling combustion using noise-sensitive detectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/24—Preventing development of abnormal or undesired conditions, i.e. safety arrangements
    • F23N5/245—Preventing development of abnormal or undesired conditions, i.e. safety arrangements using electrical or electromechanical means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/962—Preventing, counteracting or reducing vibration or noise by means of "anti-noise"
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the invention relates to a method for minimizing thermoacoustic Vibrations in gas turbine combustors, where a modulated injection of liquid or gaseous Fuel carried at the head stage of a premix burner becomes.
  • thermoacoustic vibrations denotes mutually rocking thermal and acoustic disturbances. High vibration amplitudes can occur, which can lead to undesirable effects, such as a high mechanical load on the combustion chamber, increased NO x emissions due to inhomogeneous combustion and even extinguishing the flame. This is particularly true for combustion systems with low acoustic damping.
  • the cooling air flowing into the combustion chamber has an important function, since the cooling air film on the combustion chamber wall has a sound-absorbing effect and thus contributes to the reduction of thermoacoustic vibrations.
  • an increasing proportion of the air is passed through the burners themselves in modern gas turbines, so the cooling air flow is reduced.
  • the problems mentioned at the outset which are associated with the undesirable vibrations, occur increasingly in such modern combustion chambers.
  • One possibility of sound insulation is to connect Helmholtz dampers in the combustion chamber hood or in the area of the cooling air supply. In tight spaces, as is typical for modern, compact combustion chambers, the placement of such dampers can be difficult. This method is therefore associated with a great deal of design effort.
  • thermoacoustic vibration amplitudes is associated with the disadvantage that the injection of fuel at the head stage is accompanied by an increase in the emission of NO x .
  • Fuel in the total fuel mass flow can be an optimal one Share of head stages for every conceivable gas turbine burner being found. With this special fuel mass flow on the one hand, the pulsations are sufficiently suppressed, on the other hand, the emissions are not yet unacceptable increased.
  • the optimal head level proportion is ever depending on the burner used and must be experimental be determined.
  • the ⁇ value is a measure of the ratio of those in the combustion chamber introduced to that of complete combustion theoretically required amount of air.
  • Gas turbine burner in of the present invention are typically used operated in a range of 1.8 ⁇ ⁇ ⁇ 2.2.
  • the additional Mass flow of fuel through the head stage increases the entire fuel mass flow is only insignificant, so that the ⁇ Number is not influenced by the additional mass flow.
  • thermoacoustic vibrations and the relative NO x emission were plotted against the ⁇ number in FIG.
  • the additional injection of a constant amount of fuel into the head stage of the burner leads to a significantly reduced pressure amplitude of the thermoacoustic vibrations.
  • the aim is to create a method for minimizing the pressure amplitude of thermoacoustic vibrations in gas turbine combustion chambers, the reduction in pressure amplitude being achieved almost without increasing the NO x emission.
  • This object is achieved according to the invention by the method for minimizing the pressure amplitude of thermoacoustic vibrations in a gas turbine of independent claim 1.
  • liquid or gaseous injection is carried out Fuel into the head stage of the gas turbine burner modulated.
  • modulated injection according to the invention understand every time varying injection of fuel.
  • the modulation can be carried out with any one Frequency.
  • the injection is preferably carried out with a Frequency between 0.3 Hz and 5 kHz, the range from 5 Hz to 20 Hz is particularly preferred.
  • the injection can here phase-independent of the pressure fluctuations in the Combustion system. Alternatively, the injection can be done in this way take place with the pressure fluctuations in a fixed Phase relationship. In this case, the phase of Pressure vibrations, for example, via a microphone in the Combustion chamber determined and this phase information for control the injection used.
  • the amount of fuel injected per unit time can be varied in any way within the scope of the present invention.
  • duty cycle expresses the ratio of t addition to ⁇ in percent. With a duty cycle of 50%, the period of additional fuel injection is therefore the period in which no additional fuel is injected. The addition of a constant amount of fuel corresponds to a duty cycle of 100%.
  • the injection of fuel into the head stage of the burner takes place according to the invention with a duty cycle of less than 100%.
  • the range 1% duty duty cycle 50 50% is preferred.
  • FIG. 4 shows a plot of the NO x emission against the ⁇ number for a burner without additional fuel injection into the head stage or for a burner with modulated injection of fuel into the head stage.
  • the modulation was carried out in the manner described above with a frequency of 12 Hz. Again, a pulse of fuel was injected over a period of 8.3 ms, while no fuel was added in the following 75 ms. The average fuel addition is therefore 0.44% of the total fuel mass flow and the duty cycle is 10%.
  • the NO x emission was plotted against the ⁇ number in FIG. 5, only the range of the ⁇ number between 1.8 and 2.2 relevant for gas turbine burners being taken into account.
  • the NO x emissions were plotted for a burner with an injection of a constant portion of 4.4% of the total fuel mass flow into the head stage or for a burner with modulated injection of fuel into the head stage.
  • the fuel injection was modulated in the manner described above.
  • the values of the NO x emissions were based on the emission values without additional fuel injection, which were set to 100%.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP97810903A 1997-11-24 1997-11-24 Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbine à gaz Expired - Lifetime EP0918153B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP97810903A EP0918153B1 (fr) 1997-11-24 1997-11-24 Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbine à gaz
DE59711378T DE59711378D1 (de) 1997-11-24 1997-11-24 Verfahren zum Minimieren thermoakustischer Schwingungen in Gasturbinenbrennkammern

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810903A EP0918153B1 (fr) 1997-11-24 1997-11-24 Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbine à gaz

Publications (2)

Publication Number Publication Date
EP0918153A1 true EP0918153A1 (fr) 1999-05-26
EP0918153B1 EP0918153B1 (fr) 2004-03-03

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Application Number Title Priority Date Filing Date
EP97810903A Expired - Lifetime EP0918153B1 (fr) 1997-11-24 1997-11-24 Procédé et dispositif pour minimiser les vibrations thermoacoustiques dans les chambres de combustion de turbine à gaz

Country Status (2)

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EP (1) EP0918153B1 (fr)
DE (1) DE59711378D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1429003A2 (fr) * 2002-12-07 2004-06-16 Alstom Technology Ltd Méthode et dispositif influençant les oscillations thermoacoustiques dans les systèmes de combustion
US6834504B2 (en) 2001-07-26 2004-12-28 Alstom Technology Ltd Premix burner with high flame stability having a net-like structure within the mixing section

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1495015A (en) * 1975-09-01 1977-12-14 British Petroleum Co Monitoring and/or control of burners
US4557106A (en) * 1983-11-02 1985-12-10 Ffowcs Williams John E Combustion system for a gas turbine engine
US5428951A (en) * 1993-08-16 1995-07-04 Wilson; Kenneth Method and apparatus for active control of combustion devices

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1495015A (en) * 1975-09-01 1977-12-14 British Petroleum Co Monitoring and/or control of burners
US4557106A (en) * 1983-11-02 1985-12-10 Ffowcs Williams John E Combustion system for a gas turbine engine
US5428951A (en) * 1993-08-16 1995-07-04 Wilson; Kenneth Method and apparatus for active control of combustion devices

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6834504B2 (en) 2001-07-26 2004-12-28 Alstom Technology Ltd Premix burner with high flame stability having a net-like structure within the mixing section
EP1429003A2 (fr) * 2002-12-07 2004-06-16 Alstom Technology Ltd Méthode et dispositif influençant les oscillations thermoacoustiques dans les systèmes de combustion
EP1429003A3 (fr) * 2002-12-07 2005-04-27 Alstom Technology Ltd Méthode et dispositif influençant les oscillations thermoacoustiques dans les systèmes de combustion
US7232308B2 (en) 2002-12-07 2007-06-19 Alstom Technology Ltd. Method and device for affecting thermoacoustic oscillations in combustion systems

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Publication number Publication date
EP0918153B1 (fr) 2004-03-03
DE59711378D1 (de) 2004-04-08

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